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Aerodynamic Performance of Several Techniques for Spike-Position Control of a Blunt-Lip Nose Inlet Having Internal Contraction; Mach Numbers of 0.63 and 1.5 to 2.0

Description: Memorandum presenting a study to determine locations of pressure sensors for controlling the spike position of a blunt-lip, axisymmetric inlet with internal contraction. The inlet performance was determined at Mach numbers of 0.63 and 1.5 to 2.0 for airflow schedules corresponding to those of a given turbojet engine over a wide range of ambient temperatures. The use of the ratio of a throat static pressure to either a local total or the spike-tip total pressure provided a signal that could set … more
Date: September 17, 1957
Creator: Anderson, Arthur A. & Weinstein, Maynard I.
Partner: UNT Libraries Government Documents Department
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Estimation of Neutron Energy for First Resonance From Absorption Cross Section for Thermal Neutrons

Description: Examination of published data for some 52 isotopes indicates that the neutron energy for which the first resonance occurs is related to the magnitude of the thermal absorption cross section. The empirical relation obtained is in qualitative agreement with the results of a simplified version of the resonance theory of the nucleus of Breit-Wigner.
Date: September 17, 1951
Creator: Bogart, Donald
Partner: UNT Libraries Government Documents Department
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Abrasive Cutting of Irradiated Uranium

Description: The preparation of radioactive metallurgical specimens for microscopic examination is one of the responsibilities of the Radiometallurgy Sub-Unit. An abrasive cut-off machine development program, based upon a previous experimental model, was undertaken to provide a method for sectioning of irradiated materials without undue personnel exposure or spread of contamination and finally to provide data for the design of an abrasive cutting unit for use in the work cells in the Radiometallurgy Buildin… more
Date: September 17, 1953
Creator: Boyd, Carl L.
Partner: UNT Libraries Government Documents Department
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The Creep of Zircaloy-2 Process Tubes

Description: The creep problems associated with zircaloy-2 process tubes and the factors affecting the creep of these tubes were discussed in detail. Emphasis was placed on the determination of the tube wall thickness for an SPR tube, whose minimum thickness is limited by creep considerations. It was concluded that, at the present time, there is not enough information available to design zircaloy-2 process tubes on a realistic basis. Various experiments were suggested to supplement the creep rate testing pr… more
Date: September 17, 1956
Creator: Burgess, A. B.
Partner: UNT Libraries Government Documents Department
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Economic geology of the aluminum phosphate zone on property owned by the American Agricultural Chemical Company, land-pebble phosphate district, Florida

Description: This report presents all analytical data on the aluminum phosphate zone on lands owned by the American Agricultural Chemical Co. (A. A. C. Co.), and is one of a series of reports on lands of the companies active in the Land-Pebble Phosphate district.
Date: September 17, 1991
Creator: Cathcart, James Bachelder; McGreevy, L. J. & Coleman, A. M.
Partner: UNT Libraries Government Documents Department
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Airfoil profiles for minimum pressure drag at supersonic velocities: Application of shock-expansion theory, including consideration of hypersonic range

Description: From Summary: "A comparison of optimum profiles determined by the shock-expansion method of this report with corresponding profiles determined by the linearized-theory method of a previous report shows only small differences in shape at Mach numbers up to infinity even though the linearized theory at high supersonic Mach numbers breaks down completely insofar as the drag of the profile is concerned. Curves are presented which show that for thin airfoils the use of a trailing-edge thickness cons… more
Date: September 17, 1952
Creator: Chapman, Dean R.
Partner: UNT Libraries Government Documents Department
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Stability Investigation of a Blunt Cone and a Blunt Cylinder With a Square Base at Mach Numbers From 0.64 to 2.14

Description: Memorandum presenting a discussion of a fineness-ratio-2.6 bluff shape with an x(exp 1/10) nose and a 5 degree flare extending the entire body length and a fineness-ratio-2.5 bluff shape with an x(exp 1/10) nose and a square base with sides equal to the diameter of the cylindrical forebody tested in free flight over a range of Mach and Reynolds numbers. Time histories, cross plots of force and moment coefficients, and plots of the longitudinal-force coefficient, rolling velocity, aerodynamic ce… more
Date: September 17, 1958
Creator: Coltrane, Lucille C.
Partner: UNT Libraries Government Documents Department
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Summary of Recent External Neutron-Yield Measurements by the MnSO₄ Tank Method

Description: Report that summarizes unreported neutron-yield data for the MnSO₄ tank method. Other yield measurements had been reported in other quarterly reports prior to the completion of this one.
Date: September 17, 1954
Creator: Crandall, Walter E. & Millburn, George P.
Partner: UNT Libraries Government Documents Department
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A correlation of experimental zero-lift drag of rectangular wings with symmetrical NACA 65-series airfoil sections by means of the transonic similarity law for wings of finite aspect ratio

Description: Report presenting an application of the transonic similarity law to the correlation of the zero-lift drag of rectangular wings obtained by means of free-fall and rocket techniques. Results regarding the basic data, the modified similarity rule, correlation of data, and similarity law for swept wings are provided.
Date: September 17, 1951
Creator: Danforth, Edward C. B.
Partner: UNT Libraries Government Documents Department
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Flight Investigation of Pentaborane Fuel in Rocket Boosted 9.75-Inch-Diameter Ramjet Engine With Convergent-Divergent Exhaust Nozzle

Description: Memorandum presenting a flight test of a pentaborane-fueled air-launched ramjet engine with convergent-divergent exhaust nozzle. The engine was boosted to a Mach number of about 2.00 by a small internally housed rocket; the ramjet then accelerated to a maximum free-stream Mach number of 3.02 at an altitude of 29,500 feet.
Date: September 17, 1957
Creator: Disher, John H.
Partner: UNT Libraries Government Documents Department
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NACA Investigation of a Jet-Propulsion System Applicable to Flight

Description: "Following a brief history of the NACA investigation of jet propulsion, a discussion is given of the general investigation and analysis leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at … more
Date: September 17, 1943
Creator: Ellis, Macon C., Jr. & Brown, Clinton E.
Partner: UNT Libraries Government Documents Department
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Total-Pressure Distortion and Recovery of Supersonic Nose Inlet With Conical Centerbody in Subsonic Icing Conditions

Description: Memorandum presenting an investigation of ice formation on a full-scale unheated supersonic nose inlet in the icing tunnel to determine its effect on compressor-face total-pressure distortion and recovery. Inlet angle of attack was varied from 0 to 12 degrees, free-stream Mach number from 0.17 to 0.28, and compressor-face Mach number from 0.10 to 0.47. The addition of ice to the inlet components was found to increase total-pressure-distortion levels and decreased recovery values compared with c… more
Date: September 17, 1957
Creator: Gelder, Thomas F.
Partner: UNT Libraries Government Documents Department
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Flight Determination of the Longitudinal Stability of a 1/10-Scale Rocket-Powered Model of the Northrop MX-775A Missile at Low Lift Coefficients and Mach Numbers From 0.89 to 1.34

Description: Report presenting a flight investigation to determine the longitudinal stability of a scale model of the Northrop MX-775A missile at low lift coefficients through a range of Mach numbers. Results regarding the trimmed flight and model pitching are provided.
Date: September 17, 1952
Creator: Gillespie, Warren, Jr. & Arbic, Richard G.
Partner: UNT Libraries Government Documents Department
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Theoretical analysis of total-pressure loss and airflow distribution for tubular turbojet combustors with constant annulus and liner cross-sectional areas

Description: "Compressible and incompressible flow calculations were made of the combustor total-pressure-loss coefficient and liner airflow distribution for tubular turbojet combustors having constant annulus and liner cross-sectional areas along the combustor axis. Information on static and total pressure distribution and liner air-jet entrance angles along the length of the combustor was obtained as an intermediate step in the calculations. The calculations include the effects of heat release, annulus wa… more
Date: September 17, 1956
Creator: Graves, Charles C. & Grobman, Jack S.
Partner: UNT Libraries Government Documents Department
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Free-spinning-tunnel investigation of a 1/30-scale model of the Grumman XS2F-1 airplane: TED No. NACA DE 366

Description: Report presenting an investigation of a 1/30-scale model of the Grumman XS2F-1 airplane in the 20-foot free-spinning tunnel to determine the erect spin and recovery characteristics of the model in the design flight condition and with the center of gravity at 30 percent of the mean aerodynamic chord. Results regarding the erect spins, inverted spins, spin-recovery parachutes, influence of power, control forces, landing condition, and recommended recovery technique are provided.
Date: September 17, 1952
Creator: Healy, Frederick M.
Partner: UNT Libraries Government Documents Department
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A Semiempirical Correlation of Afterburner Combustion Efficiency and Lean-Blowout Fuel-Air-Ratio Data with Several Afterburner-Inlet Variables and Afterburner Lengths

Description: Memorandum presenting a semiempirical correlation relating combustion efficiency with afterburner-inlet variables and length for a full-scale high-performance cylindrical turbojet afterburner using JP-4 fuel. The combustion efficiency in this correlation is expressed in terms of afterburner-inlet total temperature, total pressure, velocity, afterburner fuel-air ratio, and afterburner combustion-chamber length.
Date: September 17, 1957
Creator: King, Charles R.
Partner: UNT Libraries Government Documents Department
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Investigation of Wingless Missile Configurations with Folding Controls and Low-Aspect-Ratio Stabilizing Surfaces

Description: Results regarding a wind-tunnel investigation of wingless missile configurations with cylindrical bodies and conical or hemispherical noses, extensible control surfaces aft of the nose, and tails consisting of eight low-aspect-ratio triangular or rectangular fins. Normal-force, axial-force, and pitching-moment coefficients were obtained for several control deflections for Mach numbers 1.2 and 1.9.
Date: September 17, 1958
Creator: Lazzeroni, Frank A.
Partner: UNT Libraries Government Documents Department
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Investigation of Ejection Releases of an MB-1 Rocket From a 0.04956-Scaled Model of the Convair F-106A Airplane at Several Mach Numbers and Simulated Altitudes

Description: "As a continuation of an investigation of the ejection release characteristics of an internally carried MB-1 rocket in the Convair F-106A airplane, fin modifications at additional Mach numbers and simulated altitudes have been studied in the 27- by 27-inch preflight jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va. The MB-1 rocket was ejected with fins open, fins closed, fins closed with a shroud around the fins, and fins folded with a "boattail" placed in between th… more
Date: September 17, 1957
Creator: Lee, John B. & Basford, Robert C.
Partner: UNT Libraries Government Documents Department
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Investigation of Ejection Releases of an MB-1 Rocket From a 0.04956-Scaled Model of the Convair F-106A Airplane at Several Mach Numbers and Simulated Attitudes : Coord. No. AF-AM-57

Description: Memorandum presenting a study of fin modifications as a continuation of an investigation of the ejection release characteristics of an internally carried MB-1 rocket in the Convair F-106A airplane. The rocket was ejected with fins open, fins closed, fins closed with a shroud between the fins, and fins folded with a "boattail" placed in between the fins. Ejections at three different Mach numbers, and a comparison of the results at supersonic and subsonic Mach numbers are provided.
Date: September 17, 1957
Creator: Lee, John B. & Basford, Robert C.
Partner: UNT Libraries Government Documents Department
open access

Measurement of High Temperature : [bibliography]

Description: "This bibliography is limited to book and journal references covering methods and instruments in general for measuring high temperatures. The search included only literature from 1950 to the present [1957]."
Date: September 17, 1957
Creator: Maynard, G. R.
Partner: UNT Libraries Government Documents Department
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